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[Federal Register Volume 78, Number 102 (Tuesday, May 28, 2013)]
[Rules and Regulations]
[Pages 31835-31836]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-12534]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. FAA-2013-0148; Special Conditions No. 25-490-SC]

Special Conditions: Embraer S.A., Model EMB-550 Airplane; Landing 
Pitchover Condition

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for the Embraer S.A. Model 
EMB-550 airplane. This airplane will have a novel or unusual design 
feature associated with landing loads due to the automatic braking 
system. The applicable airworthiness regulations do not contain 
adequate or appropriate safety standards for this design feature. These 
special conditions contain the additional safety standards that the 
Administrator considers necessary to establish a level of safety 
equivalent to that established by the existing airworthiness standards.

DATES: Effective Date: June 27, 2013.

FOR FURTHER INFORMATION CONTACT: Todd Martin, FAA, Airframe and Cabin 
Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft 
Certification Service, 1601 Lind Avenue SW., Renton, Washington, 98057-
3356; telephone 425-227-1178; facsimile 425-227-1232.

SUPPLEMENTARY INFORMATION: 

Background

    On May 14, 2009, Embraer S.A. applied for a type certificate for 
their new Model EMB-550 airplane. The Model EMB-550 airplane is the 
first of a new family of jet airplanes designed for corporate flight, 
fractional, charter, and private owner operations. The aircraft has a 
conventional configuration with low wing and T-tail empennage. The 
primary structure is metal with composite empennage and control 
surfaces. The Model EMB-550 airplane is designed for 8 passengers, with 
a maximum of 12 passengers. It is equipped with two Honeywell HTF7500-E 
medium bypass ratio turbofan engines mounted on aft fuselage pylons. 
Each engine produces approximately 6,540 pounds of thrust for normal 
takeoff. The primary flight controls consist of hydraulically powered 
fly-by-wire elevators, aileron and rudder, controlled by the pilot or 
copilot sidestick.
    The Model EMB-550 airplane is equipped with an automatic braking 
system. This feature is a pilot-selectable function that allows earlier 
braking at landing without pilot pedal input. When the autobrake system 
is armed before landing, it automatically commands a pre-defined 
braking action after the main wheels touch down. This might cause a 
high nose gear sink rate, and potentially higher gear and airframe 
loads than would occur with a traditional braking system. Therefore, 
the FAA has determined special conditions are necessary.

Type Certification Basis

    Under the provisions of 14 CFR 21.17, Embraer S.A. must show that 
the Model EMB-550 airplane meets the applicable provisions of part 25, 
as amended by Amendments 25-1 through 25-127 thereto.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., 14 CFR part 25) do not contain adequate or 
appropriate safety standards for the Model EMB-550 airplane because of 
a novel or unusual design feature, special conditions are prescribed 
under the provisions of Sec.  21.16.
    Special conditions are initially applicable to the model for which 
they are issued. Should the type certificate for that model be amended 
later to include any other model that incorporates the same or similar 
novel or unusual design feature, the special conditions would also 
apply to the other model under Sec.  21.101.
    In addition to the applicable airworthiness regulations and special

[[Page 31836]]

conditions, the Embraer S.A. Model EMB-550 airplane must comply with 
the fuel vent and exhaust emission requirements of 14 CFR part 34 and 
the noise certification requirements of 14 CFR part 36 and the FAA must 
issue a finding of regulatory adequacy under Sec.  611 of Public Law 
92-574, the ``Noise Control Act of 1972.''
    The FAA issues special conditions, as defined in 14 CFR 11.19, in 
accordance with Sec.  11.38, and they become part of the type-
certification basis under Sec.  21.17(a)(2).

Novel or Unusual Design Features

    The Embraer S.A. Model EMB-550 airplane is equipped with an 
automatic braking system, which is a pilot-selectable function that 
allows earlier maximum braking at landing without pilot pedal input. 
When the autobrake system is armed before landing, it automatically 
commands maximum braking at main wheels touchdown. This will cause a 
high nose gear sink rate, and potentially higher gear and airframe 
loads than would occur with a traditional braking system.

Discussion

    These special conditions define a landing pitchover condition that 
accounts for the effects of the automatic braking system. The special 
conditions define the airplane configuration, speeds, and other 
parameters necessary to develop airframe and nose gear loads for this 
condition. The special conditions require that the airplane be designed 
to support the resulting limit and ultimate loads as defined in Sec.  
25.305.

Discussion of Comments

    Notice of proposed special conditions No. 25-13-01-SC for the 
Embraer S.A. Model EMB-550 airplanes was published in the Federal 
Register on February 19, 2013 (78 FR 11609). No comments were received, 
and the special conditions are adopted as proposed.

Applicability

    As discussed above, these special conditions are applicable to the 
Embraer S.A. Model EMB-550 airplane. Should Embraer S.A. apply at a 
later date for a change to the type certificate to include another 
model incorporating the same novel or unusual design feature, the 
special conditions would apply to that model as well.

Conclusion

    This action affects only certain novel or unusual design features 
on one model of airplanes. It is not a rule of general applicability.

List of Subjects in 14 CFR Part 25

    Aircraft, Aviation safety, Reporting and recordkeeping 
requirements.

    The authority citation for these special conditions is as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701, 44702, 44704.

The Special Conditions

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following special conditions are issued as part of 
the type certification basis for Embraer S.A. Model EMB-550 airplanes.

Landing Pitchover Condition

    A landing pitchover condition must be addressed that takes into 
account the effect of the autobrake system. The airplane is assumed to 
be at the design maximum landing weight, or at the maximum weight 
allowed with the autobrake system on. The airplane is assumed to land 
in a tail-down attitude and at the speeds defined in Sec.  25.481. 
Following main gear contact, the airplane is assumed to rotate about 
the main gear wheels at the highest pitch rate allowed by the autobrake 
system. This is considered a limit load condition from which ultimate 
loads must also be determined. Loads must be determined for critical 
fuel and payload distributions and centers of gravity. Nose gear loads, 
as well as airframe loads, must be determined. The airplane must 
support these loads as described in Sec.  25.305.

    Issued in Renton, Washington, on May 21, 2013.
Jeff Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-12534 Filed 5-24-13; 8:45 am]
BILLING CODE 4910-13-P
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